综合热力学模型的平流层飞艇上升轨迹优化

针对平流层飞艇的上升轨迹优化问题,综合热力学模型进行了研究.主要分析了飞艇基本热力学行为,研究了蒙皮及内部气体的能量方程并建立了详细的飞艇动力学和运动学模型.在热力学、动力学和运动学分析的基础上,建立了以飞行时间为优化目标的平流层飞艇的轨迹优化模型.利用直接配点法将轨迹优化问题转化为非线性优化问题,再通过非线性求解器SNOPT(Sparse Nonlinear Optimizer)对不同场景的问题进行最优化轨迹求解.优化结果表明:热力学效应对优化轨迹有较大影响,在上升过程中,太阳能辐射为主要影响因素,另外风场也对换热量有一定影响.     

高空气球热力学模型与上升过程仿真分析

基于对高空气球热力学环境的分析,建立了热力学与动力学耦合的高空气球动力学模型;并采用该模型对某高空气球的上升与驻留过程进行仿真分析.结果表明:高空气球上升过程中内部氦气存在"超冷"现象,其中平流层区域"超冷"明显,氦气平均温差为-19 K;由于"超冷",其上升速度曲线呈双"V"形变化;强太阳辐射与弱对流环境使驻留过程中氦气呈现"超热"现象,平衡时氦气平均温度比环境温度高39 K,球内氦气超压648.8 Pa.数值仿真的速度、平均温度变化规律与相关飞行试验数据相吻合,说明该仿真模型是有效的.      

一种基于地转风模型的平流层风场插值方法

平流层风场水平分量的数据精度和密度对高空气球实验的轨迹预测精度和飞行控制精度有着直接的影响。面向平流层风场，提出一种基于地转风模型的插值方法。该方法通过改进科里奥利频率公式，并用二维卷积计算地转风模型，提升了地转风模型的计算效率和低纬度地区风场精度，再用迭代二元线性回归和改进的自适应观测场偏差权重矩阵减小了观测误差对插值结果的影响。实验结果表明:所提插值方法能有效提升平流层风场插值计算速度，并对平流层风场水平分量的插值精度有显著提升。      

考虑风场条件的一类平流层飞艇返回过程建模与航迹规划研究

对一类气囊内外压差恒定的平流层软式飞艇,在考虑大气密度、温度变化以及大气风场的基础上,建立了飞艇三维空间运动的动力学模型;并针对能量消耗最少和航行时间最短两个指标函数,利用高斯伪谱法设计了飞艇从平流层返回地面的航迹,并对飞艇飞行高度、速度以及推力等状态变化进行分析研究.     

基于平流层风场预测的浮空器轨迹控制

平流层风场环境对浮空器设计和轨迹控制具有重要影响。针对平流层风场建模,以长沙地区2005—2010年的风场数据为例,首先采用本征正交分解（POD）方法对风场数据进行降阶处理;然后分别采用Fourier级数与BP神经网络算法对平流层风场进行预测,并对2种模型的预测精度进行比较分析;最后通过建立临近空间浮空器的动力学模型和高度调控模型,分析2种风场预测模型对浮空器轨迹控制的影响。研究结果表明,相对于Fourier预测模型,基于BP神经网络预测模型的预测精度更高,可信度更强,能够更好地为浮空器飞行轨迹控制提供参考价值。      

基于深度强化学习的平流层浮空器高度控制

为研究基于深度强化学习的平流层浮空器高度控制问题。建立平流层浮空器动力学模型，提出一种基于深度Q网络（DQN）算法的平流层浮空器高度控制方法，以平流层浮空器当前速度、位置、高度差作为智能体的观察状态，副气囊鼓风机开合时间作为智能体的输出动作，平流层浮空器非线性动力学模型与扰动风场作为智能体的学习环境。所提方法将平流层浮空器的高度控制问题转换为未知转移概率下连续状态、连续动作的强化学习过程，兼顾随机风场扰动与速度变化约束，实现稳定的变高度控制。仿真结果表明：考虑风场环境对浮空器影响下，DQN算法控制器可以很好的实现变高度的跟踪控制，最大稳态误差约为10 m，与传统比例积分微分（PID）控制器对比，其控制效果和鲁棒性更优。     

高空系留气球建模与稳定性分析

平流层高空系留气球是典型的无控制欠阻尼自治系统,因此平台本身应当具有较好的稳定性,然而该系统的线性化模型含有零特征根,导致经典的Lyapunov第一方法难以从理论上获得其稳定性结论.从一般刚体的Newton-Euler方程出发,根据刚体对任一点的平动和转动方程,建立基于广义坐标的高空系留气球二阶非线性动力学模型,并针对Lyapunov方法证明稳定性的局限性,从能量的角度运用拉格朗日定理证明了高空系留气球的稳定性,数值仿真结果与理论结果一致.     

A comprehensive numerical model investigating the thermal-dynamic performance of scientific balloon

The increase of balloon applications makes it necessary for a comprehensive understanding of the thermal and dynamic performance of scientific balloons. This paper proposed a novel numerical model to investigate the thermal and dynamic characteristics of scientific balloon in both ascending and floating conditions. The novel model consists of a dynamic model and thermal model, the dynamic model was solved numerically by a computer program developed with Matlab/Simulink to calculate the velocity and trajectory, the thermal model was solved by the Fluent program to find out the balloon film temperature distribution and inner Helium gas velocity and temperature field. These models were verified by comparing the numerical results with experimental data. Then the thermal and dynamic behavior of a scientific balloon in a real environment were simulated and discussed in details.     

高压高剪切率下密封环缝隙流体动态润滑特性

为减少高压高剪切率下热效应对密封环缝隙流体润滑性能的影响,以密封环缝隙流体剪切速度梯度、壁面剪切应力和油膜温升表征摩擦副润滑性能,采用RNG k-ε湍流模型,通过Workbench建立流-固-热多场模型,计算得到不同主轴转角下缝隙流动形态变化规律和温升前后油膜厚度变化量、不同L型槽内外径比及长径比下流速流型分布规律、壁面剪切应力、温度分布和热变形量。研究结果表明:密封环L型槽黏性底层随剪切速度增大而增厚,油膜厚度随运动周期增加而变薄;当L型槽内外径比小于1.07时,随比值减小密封环壁面剪切应力不断增大,最大变化率为7%;密封环L型槽长径比在0.19时平均壁面剪切应力达到最大,当长径比继续增大时,油膜区剪切速度梯度逐渐减小,油膜温升和热变形亦随之减小。研究结果可为马达优化以减少能量损失和改善密封环润滑条件提供理论指导和依据。      

High altitude flights in equatorial regions

A thorough analysis of balloon flights made from Hyderabad, India (Latitude 17°28′N, Longitude 78°35′E), and other equatorial sites has been made. It has been shown that limited success is expected for flights made from equatorial latitudes with balloons made out of natural colour polyethylene film, since the best known balloon film in the world today viz. Winzen Stratofilm is tested for low temperature brittleness only at ?80°C., whereas the tropopause temperatures over equatorial latitudes vary between ?80°C and ?90°C. The success becomes even more critical when flights are made with heavy payloads and larger balloons particularly at night when in the absence of solar radiation the balloon film becomes more susceptible to low temperature brittle failure. It is recommended that in case of capped balloons longer caps should be used to fully cover the inflated protion of the balloon at the higher level equatorial tropopause. It is also advised that the conditions such as wind shears in the tropopause should be critically studied before launching and a day with the tropopause temperature nearer to ?80°C should be chosen. Special care also should be taken while handling the balloon on ground and during launching phase. Properties of Winzen Stratofilm have been critically studied and fresh mandates have been recommended on the basis of limiting values of film stresses which caused balloon failures in the equatorial tropopause. It is also emphasized that the data on such flights is still meagre especially for flights with heavy payloads and larger balloons. It has been also shown that it is safest to use balloons made out of grey coloured film which retains its flexibility with the absorption of solar radiation, the success obtained with such balloons so far being 100%. The drawback, however, is that these balloons cannot be used for night flights. Stratospheric wind regimes over Hyderabad are also discussed with a view to determine the period over which long duration flights can be made. The data available, however, is meagre and it is recommended that more frequent special wind ascents be made to collect adequate statistical data from which reliable conclusions could be drawn through critical analysis.     

A challenge to the highest balloon altitude

Development of a balloon to fly at higher altitudes is one of the most attractive challenges for scientific balloon technologies. After reaching the highest balloon altitude of 53.0 km using the 3.4 μm film in 2002, a thinner balloon film with a thickness of 2.8 μm was developed. A 5000 m³ balloon made with this film was launched successfully in 2004. However, three 60,000 m³ balloons with the same film launched in 2005, 2006, and 2007, failed during ascent. The mechanical properties of the 2.8 μm film were investigated intensively to look for degradation of the ultimate strength and its elongation as compared to the other thicker balloon films. The requirement of the balloon film was also studied using an empirical and a physical model assuming an axis-symmetrical balloon shape and the static pressure. It was found that the film was strong enough. A stress due to the dynamic pressure by the wind shear is considered as the possible reason for the unsuccessful flights. A 80,000 m³ balloon with cap films covering 9 m from the balloon top will be launch in 2011 to test the appropriateness of this reinforcement.     

The VEGA Venus balloon experiment

In June 1985, two instrumented balloons were placed in the atmosphere of Venus as part of the VEGA mission. Each balloon traveled about 30 percent of the way around the planet at a float altitude near 54 kilometers. In situsensors measured pressure, temperature, vertical wind velocity, cloud particle backscatter, ambient light level, and frequency of lightning. A ground-based network of 20 radio antennas tracked the balloons by very long baseline interferometry (VLBI) techniques to monitor the Venus winds. The history, organization, and principal characteristics of this international balloon experiment are described.     

双系缆气球绳网系统的建模、配平及稳定性

为研究一种双系缆气球绳网系统的气球、绳网的设计问题和系统抗风能力的评估问题,建立了考虑风影响的双系缆气球绳网系统的数学模型,其中包括在体轴系下建立的气球的数学模型、根据无限细化理论建立的系缆的数学模型和按照一定的简化假设建立的绳网的数学模型;在配平状态下引入小扰动假设,使非线性方程组线化,并分析了该系统对阶跃风扰动的响应和稳定性.仿真计算结果表明该系统的设计合理并具有一定的抗风能力.      

单流体二维太阳风结构的磁流体力学模拟

在添加动量项的条件下，对单流体二维磁流体力学方程组进行模拟，得到了子午面上的太阳风结构，结果表明，添加动量项的形式及其被加入的位置对远区太阳风速度和质子密度有重要的影响。本文在适当的区域加入合适的动量项得出了远区太阳风速和质子密度与Ulysses观测基本符合的结果。文中给出了较合适的动量添加区域为3.5-10Rs(Rs为太阳半径）。     

A comprehensive numerical model examining the thermal performance of airships

A novel computational model for analyzing the airship’s transient thermal performance under different environmental conditions was developed. Radiative heat transfer and natural convection inside the airship were modeled using the control volume method. The Semi-Implicit Method aiming at the Pressure-Linked Equations algorithm was adopted to solve the control equations. Such approach was able to take into account the solar irradiative heat flux, the infrared radiation at different locations, and the convection both inside and outside the airship. The simulation results, showing the detailed distributions of temperature and velocity on the envelope and inside the airship, were in good agreement with the experimental measurements. The influences of solar position and material radiative properties on temperature distribution, as well as natural convective flow inside airship, were further simulated and discussed.